Control system and process for several actuators

• US 7,031,810 B2
• Filed: 04/08/2003
• Issued: 04/18/2006
• Est. Priority Date: 04/10/2002
• Status: Expired due to Term

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: Foch, Etienne, Fleury, Christophe
• Primary Examiner(s): Black, Thomas G.
• Assistant Examiner(s): Behncke, Christine M.
• Application Number:
  US10/409,761
• Publication Number:
  US 20030195673A1
• Time in Patent Office: 1,106 Days
• Field of Search: 701/3, 701/39, 244/195, 244/75.R, 244/160, 244/75.1, 700/22, 700/21, 700/20
• US Class Current: 701/3
• CPC Class Codes: G05B 9/03 with multiple-channel loop, i.e. redundant control systems

Abstract

This invention relates to a system for controlling several actuators (Al1, . . . , Anr), comprising at least two computers (L1, L2, . . . , Lk) and at least two means (C1, C2, . . . , Cn) of controlling at least one actuator, each control module being capable of controlling at least one actuator through at least one first connection (16) and being capable of receiving information about this at least one actuator through at least one second connection (15), in which each control module is connected to at least two computers through at least two first communication buses (11, 12, 13).

Claims

1. System for controlling the electrical generation system of an aircraft, said system comprising:

a plurality of actuators for the electrical generation system of the aircraft, said actuators controlling distinct outputs;

at least two computers; and

at least two modules for controlling at least one actuator, each control module being capable of controlling at least one actuator through at least one first connection and being capable of receiving information about said at least one actuator through at least one second connection, wherein each control module is connected to at least two computers through at least two first communication buses.

2. System according to claim 1, in which the computers are connected to each other through at least one second communication bus.

3. System according to claim 2, wherein each computer is connected to a communication bus through a connection.

4. System according to claim 1, wherein buses are CAN buses.

5. System according to claim 1, comprising electrical sources/generators, primary AC circuits of two contactors, controls for these contactors, and electrical distribution lines.

6. System according to claim 1, wherein the control modules are connected to communication networks, to which the computers are connected, the computers being connected to each other through an inter-computer network.

7. System according to claim 1, wherein actuators are electrical contactors.

8. System according to claim 1, wherein if a connection between a computer and an actuator is interrupted, said connection providing information concerning said actuator, said computer is capable of receiving the information concerning said actuator from another computer which is linked to said actuator.

9. Process for controlling the electrical generation system of an aircraft in a system comprising a plurality of actuators, at least two computers, and at least two modules for controlling at least one of said plurality of actuators for the electrical generation system of the aircraft, each control module being capable of controlling at least one actuator through at least one first connection and being capable of receiving information related to this at least one actuator through at least one second connection, wherein at least two control modules are used that make decisions related to control of the actuators that they control as a function of information received from several computers, and wherein each computer is capable of using information output from the control modules connected to it, calculates set values as a function of this information, and sends these set values to the said control modules, and wherein said actuators control distinct outputs of the electrical generation system of the aircraft.

10. Process according to claim 9, in which the computers work independently and asynchronously.

11. Process according to claim 9, wherein each computer is capable of accessing information originating from all actuators, even if connections between this computer and the actuator control modules are interrupted, and wherein said computer is capable of continuing to calculate set values corresponding to the different actuators and capable of sending set values related to actuators controlled by control modules for which the connection with said computer is not interrupted, on its communication bus.

12. Process according to claim 9, wherein if a connection between a computer and an actuator is interrupted, said connection providing information concerning said actuator, said computer is capable of receiving the information from another computer which is linked to said actuator.

13. Process for controlling the electrical generation system of an aircraft in a system comprising a plurality of actuators, at least two computers, and at least two modules for controlling at least one actuator, said process comprising:

controlling, using the control module, at least one of said plurality of actuators for the electrical generation system of the aircraft through at least one first connection;

receiving, at the control modules, information related to said at least one actuator through at least one second connection;

making, using at least two control modules, decisions related to control of the actuators that they control, as a function of information received from several computers;

calculating, at the computers, set values as a function of information output from the control modules connected thereto,

sending the set values to the control modules; and

controlling, using the actuators, distinct outputs of the electrical generation system of the aircraft.

14. Process according to claim 13, if a connection between a computer and an actuator is interrupted, said connection providing information concerning said actuator, said process further comprising:

receiving, at said computer, the information concerning said actuator from another computer which is linked to said actuator.